Characteristic verification and parameter optimization of airbags cushion system for airborne vehicle

Hong-yan, Wang; Hong, Huangjie; Gui-xiang, Hao; Deng, Huaxia; Qiang, Rui; Li, Jian‐Yang

doi:10.3901/cjme.2014.01.050

Cited by 10 publications

(6 citation statements)

References 1 publication

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“…A Moony Rivlin material model was used there. In [6], the landing process is simulated using FEM in the LS-DYNA software package in order to further optimize it. The same package is used in works [7,8] whose authors compare the method of corpuscular particles with the method of volume control and study the effect of mass flow, compression, and the thickness of an airbag on its effectiveness.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Spectral solution to a problem on the axisymmetric nonlinear deformation of a cylindrical membrane shell due to pressure and edges convergence

Myntiuk

2021

EEJET

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A geometrically and physically nonlinear model of a membrane cylindrical shell, which has been built and tested, describes the behavior of a airbag made of fabric material. Based on the geometrically accurate relations of "strain-displacement", it has been shown that the equilibrium equations of the shell, written in terms of Biot stresses, together with boundary conditions acquire a natural physical meaning and are the consequences of the principle of virtual work. The physical properties of the shell were described by Fung’s hyper-elastic biological material because its behavior is similar to that of textiles. For comparison, simpler hyper-elastic non-compressible Varga and Neo-Hookean materials, the zero-, first-, and second-order materials were also considered. The shell was loaded with internal pressure and convergence of edges. The approximate solution was constructed by an spectral method; the exponential convergence and high accuracy of the equilibrium equations inherent in this method have been demonstrated. Since the error does not exceed 1 % when keeping ten terms in the approximations of displacement functions, the solution can be considered almost accurate. Similar calculations were performed using a finite element method implemented in ANSYS WB in order to verify the results. Differences in determining the displacements have been shown to not exceed 0.2 %, stresses – 4 %. The study result has established that the use of Fung, Varga, Neo-Hookean materials, as well as a zero-order material, lead to similar values of displacements and stresses, from which displacements of shells from the materials of the first and second orders significantly differ. This finding makes it possible, instead of the Fung material whose setting requires a significant amount of experimental data, to use simpler ones – a zero-order material and the Varga material

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Section: Literature Review and Problem Statementmentioning

confidence: 99%

Spectral solution to a problem on the axisymmetric nonlinear deformation of a cylindrical membrane shell due to pressure and edges convergence

Myntiuk

2021

EEJET

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“…Due to the high cost and risk of the airdrop test (Wang et al , 2014), most studies use analytical and simulation analysis. But, due to the complexity of the armored vehicle model, the analysis generally describes the armored vehicle with rigid body model or rigid–flexible coupling model.…”

Section: Introductionmentioning

confidence: 99%

Landing cushioning analysis of new generation heavy airborne armored vehicles

Lu,

Chen,

Wang

et al. 2024

AEAT

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Purpose The purpose of this study is to ensure the successful implementation of a landing cushion for the new generation armored vehicles with significantly enhanced quality. Furthermore, to introduce a high-precision landing cushioning analysis model. Design/methodology/approach To accurately analyze the cushioning performance of the new generation armored vehicles, a nonlinear finite element dynamics model considering the complex travel system was established. The model considered the influence of various nonlinear factors to measure the dynamic response difference between the proposed and traditional models. The cushioning performance of airbags under different landing conditions and their various influence factors were analyzed. Findings The travel system has a large influence on the key points of the vehicle, whose rear end of the upper deck has a larger acceleration fluctuation compared with the traditional model. The increase in the body material stiffness is helpful to reduce this fluctuation. The established nonlinear finite element model can effectively analyze the landing cushioning performance of airborne armored vehicles. The area of the external airbag vent has a large influence on the cushioning performance, and the cushioning system has excellent cushioning performance under various operating conditions. Practical implications This study introduces the travel system, which is ignored by traditional analytical models. The interactions between various types of complex structures are included in the analysis process in its entirety, leading to valuable new conclusions. Quantitatively reveals the analytical errors of traditional simulation models in multiple dimensions and the reasons for their formation. Based on a high-precision simulation model, it is verified that the designed airbag cushioning system has an excellent cushioning effect for the new generation of heavy airborne armored vehicles. Originality/value The novelty of this work comes from the need for smooth landing with low overload for a new type of large-load airborne armored vehicle and provides a high-precision model that quantifies the traditional analytical modeling errors and error principle.

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“…Due to the advantages of foldability, reusability, light weight, high reliability and superior cushioning performance, cushion airbags are applied as one of landing buffer devices for many returnable spacecrafts. The cushion airbag is an inflatable structure that utilizes the elastic deformation of flexible materials, compression of internal gas, and gas exhausting to absorb the kinetic energy of a returnable spacecraft during the landing attenuation process, achieving deceleration, reducing impact overload, and protecting returnable spacecrafts [1,2].…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

Xu,

Yang,

Huang

et al. 2024

Aerospace

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To improve the cushioning performance of soft-landing systems, a novel origami-inspired combined cushion airbag is proposed. The geometry size, initial pressure, and exhaust vent area of the cushion airbags are designed preliminarily using a theoretical model. The finite element models, including the returnable spacecraft and cushion airbags, are established via the control volume method (CVM) to analyze the impact dynamic behavior and cushioning performance during the landing attenuation process. The cushioning performance of the cushion airbags in complex landing environments are studied to investigate the influence of horizontal velocity, lateral velocity and nonhorizontal landing surfaces. Four design parameters of the cushion airbags, including the initial pressure, venting threshold pressure, exhaust vent area and polygon edge number, are employed to study their influence on the cushioning performance. A multi-objective optimization model of the cushion airbags based on the neural network and multi-objective water cycle algorithm is established to realize the rapid optimization design. The Pareto front of the maximum overload and specific energy absorption is obtained. The analysis results show that the maximum overload of the proposed combined cushion airbags is 7.30 g. The system with the anti-rollover design can avoid rollover and achieve outstanding cushioning performance in complex landing environments. The maximum overload of the returning spacecraft is decreased by 16.4% from 7.30 g to 6.10 g after multi-objective optimizations. This study could provide the technical support for the soft-landing system design of returnable spacecrafts.

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Characteristic verification and parameter optimization of airbags cushion system for airborne vehicle

Cited by 10 publications

References 1 publication

Spectral solution to a problem on the axisymmetric nonlinear deformation of a cylindrical membrane shell due to pressure and edges convergence

Spectral solution to a problem on the axisymmetric nonlinear deformation of a cylindrical membrane shell due to pressure and edges convergence

Landing cushioning analysis of new generation heavy airborne armored vehicles

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

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